[Federal Register Volume 60, Number 174 (Friday, September 8, 1995)]
[Rules and Regulations]
[Pages 46758-46760]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-20849]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-ANE-10; Amendment 39-9346; AD 95-17-15]
Airworthiness Directives; General Electric Company CF6 Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to General Electric Company (GE) CF6-45/-50 series turbofan
engines, that requires an initial and repetitive on-wing visual
inspection of the side links of the five-link forward mount assembly
for cracks, and replacement of the side links and pylon attachment
bolts, and inspection of the fail-safe bolt and platform lug, if the
side links are found cracked. This AD also requires a shop-level
refurbishment of the side links as a terminating action to the on-wing
inspection program. This amendment is prompted by four reports of
cracked side links detected during routine engine shop visits. The
actions specified by this AD are intended to prevent a side link
fracture, which could result in the failure of the second side link, or
the forward engine mount pylon attachment bolts, and possible
separation of the engine from the aircraft.
DATES: Effective October 10, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 10, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from General Electric Aircraft Engines, CF6 Distribution
Clerk, Room 132, 111 Merchant Street, Cincinnati, OH 45246. This
information may be examined at the Federal Aviation Administration
(FAA), New England Region, Office of the Assistant Chief Counsel, 12
New England Executive Park, Burlington, MA; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7136; fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to General Electric Company (GE) CF6-
45/-50 series turbofan engines was published in the Federal Register on
April 6, 1995 (60 FR 17487). That action proposed to require an initial
and repetitive on-wing visual inspection of the side links of the five-
link forward mount assembly for cracks, and replacement of the side
links and pylon attachment bolts, and inspection of the fail-safe bolt
and platform lug, if side links are found cracked. That proposal also
would require a shop-level refurbishment of the side links as a
terminating action to the on-wing inspection program. The actions would
be required to be accomplished in accordance with GE Aircraft Engines
CF6-50 Service Bulletin No. 72-1092, dated November 18, 1994.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
The one commenter states that the requirement to refurbish the side
link at the next engine shop visit after effective date of the AD
identified in paragraph (b) should be extended so that their current
maintenance program is not disrupted.
[[Page 46759]]
The commenter further feels that the initial and repetitive
inspection program will be sufficient to meet the safety objectives of
the AD, and therefore considers the refurbishment to be optional. The
FAA does not concur. The FAA has determined that the refurbishment
compliance schedule fairly and reasonably balances the safety need to
eliminate the unsafe condition from the fleet as quickly as possible
with the operators' need to avoid unscheduled maintenance actions. The
initial and repetitive inspections were intended as an interim
corrective action only, and in order to meet the safety objectives of
the AD, the refurbishment was deemed necessary. Individual operators
who believe their circumstances warrant relief from the compliance
schedule may submit requests for alternative methods of compliance or
adjustments to the compliance times.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
The FAA estimates that 220 engines installed on aircraft of U.S.
registry will be affected by this AD, that it will take approximately
7.5 work hours per engine to accomplish the required actions, and that
the average labor rate is $60 per work hour. The FAA has estimated that
only a small percentage of parts will actually require replacement as a
result of this AD, and therefore, has determined the parts cost to be
negligible. Based on these figures, the total cost impact of the AD on
U.S. operators is estimated to be $99,000.
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-17-15 General Electric Company: Amendment 39-9346. Docket 95-ANE-
10.
Applicability: General Electric Company (GE) CF6-45/-50 series
turbofan engines installed on, but not limited to, Airbus A300
series, Boeing 747 series, and McDonnell Douglas DC-10 series
aircraft.
Note: This airworthiness directive (AD) applies to each engine
identified in the preceding applicability provision, regardless of
whether it has been modified, altered, or repaired in the area
subject to the requirements of this AD. For engines that have been
modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must use the
authority provided in paragraph (d) to request approval from the
Federal Aviation Administration (FAA). This approval may address
either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe
condition described in this AD. Such a request should include an
assessment of the effect of the changed configuration on the unsafe
condition addressed by this AD. In no case does the presence of any
modification, alteration, or repair remove any engine from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously. To prevent a side link fracture, which could result in
failure of the second side link, or the forward engine mount pylon
attachment bolts, and possible separation of the engine from the
aircraft, accomplish the following:
(a) Inspect left-hand side links, Part Numbers (P/N) 9204M94P01,
9204M94P03, and 9346M99P01, and right-hand side links, P/N's
9204M94P02, 9204M94P04, and 9346M99P02, that have not had the side
link refurbishment done in accordance with GE CF6-50 Task Numbered
Shop Manual, GEK 50481, Chapter 72-23-11, including Temporary
Revision No. 72-0821 and 72-0822, both dated November 1, 1994, as
follows:
(1) For side links that have not been previously inspected in
accordance with GE Aircraft Engines (GEAE) CF6-50 Service Bulletin
(SB) No. 72-1092, dated November 18, 1994, inspect in accordance
with paragraph 2.A of GEAE CF6-50 SB No. 72-1092, dated November 18,
1994, prior to accumulating 350 cycles in service (CIS), or 750
hours time in service (TIS), after the effective date of this AD,
whichever occurs earlier.
(2) For side links that have been previously inspected in
accordance with GEAE CF6-50 SB No. 72-1092, dated November 18, 1994,
inspect in accordance with paragraph 2.A of GEAE CF6-50 SB No. 72-
1092, dated November 18, 1994, prior to accumulating 350 CIS, or 750
hours TIS since inspected in accordance with GEAE CF6-50 SB No. 72-
1092, dated November 18, 1994, whichever occurs earlier.
(3) Thereafter, inspect in accordance with paragraph 2.A of GEAE
CF6-50 SB No. 72-1092, dated November 18, 1994, at intervals not to
exceed 350 CIS, or 750 hours TIS since the last inspection,
whichever occurs earlier.
(4) If side links are found cracked, replace the cracked side
links and pylon attachment bolts with serviceable parts, and inspect
the fail-safe bolt and platform lug in accordance with paragraph 2.B
of GEAE CF6-50 SB No. 72-1092, dated November 18, 1994, prior to
further flight.
(b) Refurbish the left-hand and right-hand side links identified
in paragraph (a) of this AD at the next engine shop visit after the
effective date of this AD in accordance with paragraph 2.C of GEAE
CF6-50 SB No. 72-1092, dated November 18, 1994. Refurbishment of
side links in accordance with this paragraph constitutes terminating
action to the on-wing inspection requirements of paragraph (a) of
this AD.
(c) For the purpose of this AD, an engine shop visit is defined
as the induction of an engine into a shop for maintenance involving
the separation of the fan and core modules.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Engine Certification Office. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(e) The actions required by this AD shall be done in accordance
with the following service bulletin:
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Document No. Pages Date
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GEAE CF6-50 SB No. 72-1092............... 1-7 Nov. 18, 1994.
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[[Page 46760]]
Total Pages: 7.
This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from General Electric Aircraft
Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street,
Cincinnati, OH 45246. Copies may be inspected at the FAA, New
England Region, Office of the Assistant Chief Counsel, 12 New
England Executive Park, Burlington, MA; or at the Office of the
Federal Register, 800 North Capitol Street NW., suite 700,
Washington, DC.
(f) This amendment becomes effective on October 10, 1995.
Issued in Burlington, Massachusetts, on August 15, 1995.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 95-20849 Filed 9-7-95; 8:45 am]
BILLING CODE 4910-13-U
